Moment Produced by Vertical Tail for given Lift Curve Slope Calculator

✖The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.ⓘ Vertical Tail Moment Arm [𝒍_v]			+10% -10%
✖The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.ⓘ Vertical Tail Lift Curve Slope [C_v]			+10% -10%
✖The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.ⓘ Sideslip Angle [β]			+10% -10%
✖Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.ⓘ Sidewash Angle [σ]			+10% -10%
✖Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.ⓘ Vertical Tail Dynamic Pressure [Q_v]			+10% -10%
✖The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.ⓘ Vertical Tail Area [S_v]			+10% -10%

✖Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.ⓘ Moment Produced by Vertical Tail for given Lift Curve Slope [N_v]

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Moment Produced by Vertical Tail for given Lift Curve Slope Solution

STEP 0: Pre-Calculation Summary

Formula Used

Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area
N_v = 𝒍_v*C_v*(β+σ)*Q_v*S_v
This formula uses 7 Variables

Variables Used

Vertical Tail Moment - (Measured in Newton Meter) - Vertical Tail Moment is the moment produced by the vertical tailplane of an aircraft due to the side force acting on it.
Vertical Tail Moment Arm - (Measured in Meter) - The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical Tail Lift Curve Slope - (Measured in 1 per Radian) - The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft.
Sideslip Angle - (Measured in Radian) - The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind.
Sidewash Angle - (Measured in Radian) - Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane.
Vertical Tail Dynamic Pressure - (Measured in Pascal) - Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Vertical Tail Area - (Measured in Square Meter) - The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.

STEP 1: Convert Input(s) to Base Unit

Vertical Tail Moment Arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical Tail Lift Curve Slope: 0.7 1 per Radian --> 0.7 1 per Radian No Conversion Required
Sideslip Angle: 0.05 Radian --> 0.05 Radian No Conversion Required
Sidewash Angle: 0.067 Radian --> 0.067 Radian No Conversion Required
Vertical Tail Dynamic Pressure: 11 Pascal --> 11 Pascal No Conversion Required
Vertical Tail Area: 5 Square Meter --> 5 Square Meter No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

N_v = 𝒍_v*C_v*(β+σ)*Q_v*S_v --> 1.2*0.7*(0.05+0.067)*11*5

Evaluating ... ...

N_v = 5.4054

STEP 3: Convert Result to Output's Unit

5.4054 Newton Meter --> No Conversion Required

FINAL ANSWER

5.4054 Newton Meter <-- Vertical Tail Moment

(Calculation completed in 00.004 seconds)

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Created by Vinay Mishra

Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune

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National Institute Of Technology (NIT), Hamirpur

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< Vertical Tail Contribution Calculators

Vertical Tail Angle of Attack for given Vertical Tail Side Force

LaTeX Go Vertical Tail Angle of Attack = -(Vertical Tail Side Force/(Vertical Tail Lift Curve Slope*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Lift Curve Slope

LaTeX Go Vertical Tail Lift Curve Slope = -(Vertical Tail Side Force/(Vertical Tail Angle of Attack*Vertical Tail Dynamic Pressure*Vertical Tail Area))

Vertical Tail Side Force

LaTeX Go Vertical Tail Side Force = -Vertical Tail Lift Curve Slope*Vertical Tail Angle of Attack*Vertical Tail Area*Vertical Tail Dynamic Pressure

Vertical Tail Angle of Attack

LaTeX Go Vertical Tail Angle of Attack = Sidewash Angle+Sideslip Angle

Moment Produced by Vertical Tail for given Lift Curve Slope Formula

LaTeX Go

Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area
N_v = 𝒍_v*C_v*(β+σ)*Q_v*S_v

What is stability and control?

Control is the pilot action of moving the flight controls, providing the aerodynamic force that induces the aircraft to follow the desired flight path. Stability is the characteristic of an aircraft that tends to cause it to fly (hands-off) in a straight-and-level flightpath.

How to Calculate Moment Produced by Vertical Tail for given Lift Curve Slope?

Moment Produced by Vertical Tail for given Lift Curve Slope calculator uses Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area to calculate the Vertical Tail Moment, Moment produced by vertical tail for given lift curve slope is a measure of the rotational force generated by the vertical tail of an aircraft, calculated by multiplying the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area, providing a critical indicator of an aircraft's stability and control during flight. Vertical Tail Moment is denoted by N_v symbol.

How to calculate Moment Produced by Vertical Tail for given Lift Curve Slope using this online calculator? To use this online calculator for Moment Produced by Vertical Tail for given Lift Curve Slope, enter Vertical Tail Moment Arm (𝒍_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v) and hit the calculate button. Here is how the Moment Produced by Vertical Tail for given Lift Curve Slope calculation can be explained with given input values -> 5.4054 = 1.2*0.7*(0.05+0.067)*11*5.

FAQ

What is Moment Produced by Vertical Tail for given Lift Curve Slope?

Moment produced by vertical tail for given lift curve slope is a measure of the rotational force generated by the vertical tail of an aircraft, calculated by multiplying the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area, providing a critical indicator of an aircraft's stability and control during flight and is represented as N_v = 𝒍_v*C_v*(β+σ)*Q_v*S_v or Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area. The Vertical Tail Moment Arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The Vertical Tail Lift Curve Slope is the slope associated with the lift curve of a vertical tailplane of an aircraft, The Sideslip Angle, also called the angle of sideslip, is a term used in fluid dynamics and aerodynamics, and aviation which relates to the rotation of the aircraft centerline from the relative wind, Sidewash Angle is caused by the flow field distortion due to the wings and fuselage. It is analogous to the downwash angle for the horizontal tailplane, Vertical Tail Dynamic Pressure is the dynamic pressure associated with the vertical tail of an aircraft & The Vertical Tail Area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.

How to calculate Moment Produced by Vertical Tail for given Lift Curve Slope?

Moment produced by vertical tail for given lift curve slope is a measure of the rotational force generated by the vertical tail of an aircraft, calculated by multiplying the vertical tail moment arm, lift curve slope, sideslip angle, sidewash angle, dynamic pressure, and vertical tail area, providing a critical indicator of an aircraft's stability and control during flight is calculated using Vertical Tail Moment = Vertical Tail Moment Arm*Vertical Tail Lift Curve Slope*(Sideslip Angle+Sidewash Angle)*Vertical Tail Dynamic Pressure*Vertical Tail Area. To calculate Moment Produced by Vertical Tail for given Lift Curve Slope, you need Vertical Tail Moment Arm (𝒍_v), Vertical Tail Lift Curve Slope (C_v), Sideslip Angle (β), Sidewash Angle (σ), Vertical Tail Dynamic Pressure (Q_v) & Vertical Tail Area (S_v). With our tool, you need to enter the respective value for Vertical Tail Moment Arm, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Vertical Tail Dynamic Pressure & Vertical Tail Area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.

How many ways are there to calculate Vertical Tail Moment?

In this formula, Vertical Tail Moment uses Vertical Tail Moment Arm, Vertical Tail Lift Curve Slope, Sideslip Angle, Sidewash Angle, Vertical Tail Dynamic Pressure & Vertical Tail Area. We can use 2 other way(s) to calculate the same, which is/are as follows -

Vertical Tail Moment = -(Vertical Tail Moment Arm*Vertical Tail Side Force)
Vertical Tail Moment = Yawing Moment Coefficient*Wing Dynamic Pressure*Wingspan*Reference Area

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